CN103738496A - Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof - Google Patents
Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof Download PDFInfo
- Publication number
- CN103738496A CN103738496A CN201310722455.XA CN201310722455A CN103738496A CN 103738496 A CN103738496 A CN 103738496A CN 201310722455 A CN201310722455 A CN 201310722455A CN 103738496 A CN103738496 A CN 103738496A
- Authority
- CN
- China
- Prior art keywords
- screw propeller
- aircraft
- wing
- landing
- power system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000005183 dynamical system Methods 0.000 title 1
- 230000001360 synchronised effect Effects 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 6
- 230000000717 retained effect Effects 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000007667 floating Methods 0.000 description 2
- 206010016275 Fear Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Images
Landscapes
- Transmission Devices (AREA)
- Toys (AREA)
Abstract
本发明提供一种适用于垂直起降飞行器的动力系统结构及其控制方法，包括提供动力的螺旋桨，所述螺旋桨布置于飞机两侧主机翼的前后侧，位于主机翼前侧的螺旋桨可由竖直状态向上倾转为水平状态，位于主机翼后侧的螺旋桨可由竖直状态向下倾转为水平状态，本发明通过设计，不但实现了垂直起降模式下与现有的最为成熟稳定的X型四轴飞行器类似的布局和控制方式，而且在平飞模式下最大程度上保留传统可靠的固定翼飞机的布局形式、有效机翼面积和整体结构，所以与其他垂直起降飞行器相比具有布局形式合理，结构简单，控制方式成熟可靠，飞行更加稳定，航程更远，载重更大等优点。
The present invention provides a power system structure suitable for a vertical take-off and landing aircraft and a control method thereof, including propellers providing power, the propellers are arranged on the front and rear sides of the main wings on both sides of the aircraft, and the propellers located on the front side of the main wings can be operated by vertical The state is tilted upwards to a horizontal state, and the propeller located on the rear side of the main wing can be tilted downwards from a vertical state to a horizontal state. Through the design of the present invention, it not only realizes the vertical take-off and landing mode, but also the most mature and stable X-type The layout and control methods of the quadcopter are similar, and in the level flight mode, the layout form, effective wing area and overall structure of the traditional and reliable fixed-wing aircraft are retained to the greatest extent, so it has a layout form compared with other vertical take-off and landing aircraft. Reasonable, simple structure, mature and reliable control method, more stable flight, longer range, larger load and so on.
Description
Technical field
The invention belongs to aviation aircraft design field, be specifically related to a kind of power system structure and control method thereof that is applicable to vertically taking off and landing flyer.
Background technology
The birth of vertical takeoff and landing technology is mainly because the deficiency, the particularly performance in all previous war of aircraft rolling start mode allow the vertical takeoff and landing of aircraft enter people's sight line.The war such as World War II and Mideast Asian war directly allows people experience to the attack on enemy airport needs the weak point of the sliding race formula aircraft of runway, and cold war is the catalyst of vertical takeoff and landing technology.Five sixties after World War II, very likely breaking out under the shade of nuclear war, fears are entertained that occurs that general nuclear warfare is to the situation that airport damages, conventional airplane cannot be set out, so expedited the emergence of the vertical takeoff and landing technology of fixed wing aircraft.Vertical take-off and landing aircraft (VTOL aircraft) reduces or has substantially broken away from the dependence to runway, only need very little level land just can rise sheer from level ground and vertical landing, so aircraft can decentralized configuration in war, be convenient to launch an attack flexibly, shift and pretend hidden, be difficult for being found by enemy, the attendance rate also significantly improves, and enemy's strike is had to very high emergentness, has greatly improved the battlefield survival rate of aircraft.
There is the fixed wing aircraft of vertical takeoff and landing ability not need special airport and runway, so just saved expensive airport construction expense, need not drive bird, also can be in landing under bad weather condition, reduced use cost, but also it is far away to have voyage, the advantage that the conventional helicopters such as capacity weight height do not have.So vertical takeoff and landing Fixed Wing AirVehicle becomes a popular direction of aviation aircraft development.
Existing vertically taking off and landing flyer mostly adopts single shaft, twin shaft, or three axles etc. are controlled very difficult vertical takeoff and landing topology layout form, not only stability and reliability are all difficult to guarantee during vertical takeoff and landing pattern, and because can causing the structure of aircraft, its mode adopting is different from general conventional fixed wing aircraft, too complicated, badly influence the aerodynamic arrangement under fixed-wing pattern, thus the flight quality while having a strong impact on flat flying.Another one aspect, existing vertical take-off and landing aircraft (VTOL aircraft) major part, because its structure design is limit, is had no idea to adopt the very large span, thereby cannot be increased actv. wing area, its flight efficiency cannot be improved, and voyage is compared or differs greatly with traditional fixed wing aircraft.So, only, in the situation that adopting the most ripe cyclogyro model layout's form as far as possible and not affecting conventional fixed wing aircraft layout structure, accomplish vertical takeoff and landing function, could improve to the full extent the performance of the various aspects of vertically taking off and landing flyer.
Summary of the invention
The object of the present invention is to provide a kind of power system structure and control method thereof that is applicable to vertically taking off and landing flyer.
For achieving the above object, the present invention has adopted following technical scheme.
A kind of power system structure that is applicable to vertically taking off and landing flyer, comprise the screw propeller that power is provided, described screw propeller is arranged in the front and back side of aircraft both sides host wing, and the screw propeller that is positioned at host wing front side can upwards vert, and the screw propeller that is positioned at host wing rear side can vert downwards.
The screw propeller of described host wing front side adopts formal dress, and for aircraft provides pulling force and lift, the screw propeller of host wing rear side adopts anti-dress, for aircraft provides thrust and lift.
Before and after described host wing, side screw propeller verting separately synchronously carried out.
On the host wing of both sides, be respectively arranged with the some to screw propeller of equal number, every pair of screw propeller consists of screw propeller and a screw propeller that is arranged in respective hosts wing rear side that is arranged in respective hosts wing front side, and a pair of screw propeller adopts a corresponding driving engine to drive simultaneously or adopt two driving engines to drive respectively.
On described host wing, be provided with driving engine and hang cabin, driving engine is hung the front and back end in cabin and to host wing front and back side correspondence, is stretched out respectively, a set of power system is equipped with respectively in the front and back end in driving engine extension cabin, and power system comprises the driving engine of screw propeller and driving screw propeller, and driving engine is hung cabin with driving engine and is connected.
The control method of the above-mentioned power system structure that is applicable to vertically taking off and landing flyer, comprises the following steps:
When aircraft is flat while flying, propeller plane all in ground close to vertical state, for aircraft provides power forward; When aircraft vertical takeoff and landing and hovering, the screw propeller of synchronous driving host wing front side and rear side verts, and wherein the screw propeller of host wing front side upwards verts, and the screw propeller of host wing rear side verts downwards.
Beneficial effect of the present invention is embodied in:
The present invention adopts ripe cyclogyro model layout form and does not affect conventional fixed wing aircraft layout structure, make it more simple in structure than existing vertically taking off and landing flyer, control difficulty is low, has better vertical takeoff and landing performance and hovering performance, and has faster flying speed and farther voyage.
Adopt vertically taking off and landing flyer of the present invention duty runway not compared with traditional fixed wing aircraft, but carry out vertical and landing takeoff, greatly reduce the requirement to runway.There is flying speed faster compared with conventional helicopters, farther voyage and the flying height of Geng Gao.The present invention is by design, not only realized under vertical takeoff and landing pattern and the existing the most mature and stable similar layout of X-type four-axle aircraft and mode, and at flat distribution form, effective wing area and the integral structure that flies to retain to the full extent under pattern traditional failure-free fixed wing aircraft.So it is reasonable to have distribution form compared with other vertically taking off and landing flyer, simple in structure, the advantage such as mode mature and reliable, flies more stable, and voyage is farther, and load-carrying is larger.Its distribution form, structure and mode not only can be used for SUAV (small unmanned aerial vehicle) also can be for small-sized manned aircraft and big-and-middle-sized transport plane, and its driving engine not only can adopt electrical motor, and piston type internal combustion engine also can adopt jet engine etc.Adopt SUAV (small unmanned aerial vehicle) of the present invention and small-sized manned aircraft, be not only applicable to civil aviation transportation, disaster relief prospecting, aerial mapping, is also suitable for army individual-soldier and scouts use.And the present invention also has obvious advantage for big-and-middle-sized transport plane.
Adopt vertically taking off and landing flyer of the present invention to take into account the advantage of Fixed Wing AirVehicle and helicopter, overcome the shortcoming of other vertically taking off and landing flyer, and produced prototype and take a flight test, excellent performance, reliable and stable, there is very strong comformability, have a extensive future.
Accompanying drawing explanation
Fig. 1 adopts the monnolithic case figure of vertically taking off and landing flyer of the present invention under its level flight condition;
Fig. 2 is the monnolithic case figure of the vertically taking off and landing flyer shown in Fig. 1 under its vertical takeoff and landing and floating state;
Fig. 3 is applicable to the vertically taking off and landing flyer shown in Fig. 1 at the flat power system position view that flies state;
Fig. 4 is applicable to the power system position view of the vertically taking off and landing flyer shown in Fig. 1 under vertical takeoff and landing and floating state;
In figure: 1 is fuselage, 2 is host wing, 3 horizontal tails, and 4 is vertical fin, 5 is driving engine extension cabin, 6 is power system, and 7 is nose-gear, and 8 is main landing gear, and 51 for driving the steering wheel of servo, 52 is drive link, the 53 driven steering wheels that are driving engine, and 61 is screw propeller, 62 is driving engine.
The specific embodiment
Below in conjunction with drawings and Examples, the present invention is elaborated.
The present invention is mainly by the total arrangement to vertically taking off and landing flyer, and the appropriate design of offline mode conversion regime and the required mechanism of attitude control realizes.
Embodiment
The invention provides a kind of power system structure that is applicable to vertically taking off and landing flyer, comprise the screw propeller of power 61 is provided, described screw propeller 61 is arranged in the front and back side of aircraft both sides host wing 2, the screw propeller 61 that is positioned at host wing 2 front sides can upwards be verted for horizontality by vertical state, and the screw propeller 61 that is positioned at host wing 2 rear sides can be dipped down and be transferred to horizontality by vertical state; The screw propeller 61 of described host wing front side adopts formal dress, and for aircraft provides pulling force and lift, the screw propeller 61 of host wing rear side adopts anti-dress, for aircraft provides thrust and lift; Before and after described host wing, side screw propeller 61 verting separately synchronously carried out; Before and after described host wing, the screw propeller 61 of side adopts a driving engine to drive simultaneously or adopt two driving engines to drive respectively.Be specifically introduced with reference to the accompanying drawings below.
Shown in Fig. 1, Fig. 2, adopt vertically taking off and landing flyer of the present invention to adopt conventional formula aerodynamic arrangement: to comprise fuselage 1, host wing 2, horizontal tail 3, vertical fin 4, nose-gear 7, main landing gear 8 and each rudder face etc.Wherein on both sides host wing 2, be separately installed with a driving engine and hang cabin 5, a set of power system 6 is equipped with respectively in the front and back that hang cabin at driving engine, this power system comprises screw propeller 61 and driving engine 62, and 4 cover power systems provide vertical takeoff and landing for aircraft, power when hovering and horizontal flight altogether.
As shown in Figure 3, Figure 4, in the present invention, driving engine is hung 5 inside, cabin and is provided with bar-link drive.Bar-link drive comprises the steering wheel 51 that drives servo, and the driven steering wheel 53 of drive link 52 and driving engine drives the steering wheel 51 of servo and the driven steering wheel 53 of driving engine to be connected with drive link 52.Wherein drive the diameter of the steering wheel 51 of servo and the driven steering wheel 53 of driving engine identical, and be parallel to each other, when static and driving engine extension cabin 5 axis keep 45 degree angles, thereby before and after guaranteeing in switching process, driving engine angle synchronously changes.When aircraft is flat while flying, four screw propeller 61 planes all in ground close to plumbness, for aircraft provides power forward.When aircraft vertical takeoff and landing and hovering, the bar-link drive of hanging 5 inside, cabin by driving engine synchronously drives, two screw propellers of host wing front portion upwards vert, and two screw propellers at host wing rear portion vert downwards, thereby four screw propellers can provide lift upwards for aircraft; And the spin direction of four screw propellers and control method are similar to the four-axle aircraft of X-type, can in vertical takeoff and landing and hovering process, provide stable attitude control for aircraft.In offline mode when conversion,, four propeller planes can keep synchronously verting, and not only can offset the overbalance moment of torsion verting in the aircraft pitch direction producing, and the mode of four axles still can in the vertical direction be provided, and guarantee that aircraft is steady; The propeller plane process of verting is controlled in connection with the attitude on aircraft and airspeed sensor, thereby guarantees that it transforms in offline mode process steadily and not stall.The switching process of offline mode is when vertical take-off and landing aircraft (VTOL aircraft) is the most dangerous often, and the present invention is by controllability and safety that rationally design has improved this process greatly cleverly.
Claims (6)
1. one kind is applicable to the power system structure of vertically taking off and landing flyer, it is characterized in that: comprise the screw propeller of power (61) is provided, described screw propeller (61) is arranged in the front and back side of aircraft both sides host wings (2), the screw propeller (61) that is positioned at host wing (2) front side can upwards vert, and the screw propeller (61) that is positioned at host wing (2) rear side can vert downwards.
2. a kind of power system structure that is applicable to vertically taking off and landing flyer according to claim 1, it is characterized in that: the screw propeller (61) of described host wing (2) front side adopts formal dress, for aircraft provides pulling force and lift, the screw propeller (61) of host wing (2) rear side adopts anti-dress, for aircraft provides thrust and lift.
3. a kind of power system structure that is applicable to vertically taking off and landing flyer according to claim 1, is characterized in that: before and after described host wing (2), side screw propellers (61) verting separately synchronously carried out.
4. a kind of power system structure that is applicable to vertically taking off and landing flyer according to claim 1, it is characterized in that: on both sides host wing (2), be respectively arranged with the some to screw propeller (61) of equal number, every pair of screw propeller (61) consists of screw propeller (61) and a screw propeller (61) that is arranged in respective hosts wing rear side that is arranged in respective hosts wing front side, and a pair of screw propeller (61) adopts a corresponding driving engine to drive simultaneously or adopt two driving engines to drive respectively.
5. a kind of power system structure that is applicable to vertically taking off and landing flyer according to claim 1, it is characterized in that: on described host wing (2), be provided with driving engine and hang cabin (5), driving engine is hung the front and back end in cabin (5) and to host wing (2) front and back side correspondence, is stretched out respectively, a set of power system (6) is equipped with respectively in the front and back end in driving engine extension cabin (5), power system (6) comprises the driving engine (62) of screw propeller (61) and driving screw propeller, and driving engine is hung cabin with driving engine and is connected.
6. a control method that is applicable to as claimed in claim 1 the power system structure of vertically taking off and landing flyer, is characterized in that: comprise the following steps:
When aircraft is flat while flying, screw propeller (61) plane in ground close to vertical state, for aircraft provides power forward; When aircraft vertical takeoff and landing and hovering, the screw propeller (61) of the synchronous driving host wing (2) front side and rear side verts, and wherein the screw propeller (61) of host wing (2) front side upwards verts, and the screw propeller (61) of host wing (2) rear side verts downwards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310722455.XA CN103738496A (en) | 2013-12-24 | 2013-12-24 | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310722455.XA CN103738496A (en) | 2013-12-24 | 2013-12-24 | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103738496A true CN103738496A (en) | 2014-04-23 |
Family
ID=50495594
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310722455.XA Pending CN103738496A (en) | 2013-12-24 | 2013-12-24 | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103738496A (en) |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104494812A (en) * | 2015-01-08 | 2015-04-08 | 常州大学 | Fixed-wing air vehicle device with screw propeller having tiltable shaft |
| CN104743112A (en) * | 2015-04-24 | 2015-07-01 | 南昌航空大学 | Novel tilt wing aircraft |
| CN105292462A (en) * | 2015-10-30 | 2016-02-03 | 佛山市神风航空科技有限公司 | Multi-axle aircraft |
| CN105460233A (en) * | 2015-11-12 | 2016-04-06 | 中国人民解放军国防科学技术大学 | Method for designing fixed-wing aircraft capable of vertically taking off and landing |
| CN105539835A (en) * | 2016-01-18 | 2016-05-04 | 成都纵横自动化技术有限公司 | Composite-wing vertical take-off and landing aircraft |
| CN105564641A (en) * | 2016-01-29 | 2016-05-11 | 珠海市磐石电子科技有限公司 | Vector aircraft |
| CN106163925A (en) * | 2015-06-18 | 2016-11-23 | 罗春晖 | A kind of lift unit for aircraft and use the takeoff method of this device |
| CN106240812A (en) * | 2016-08-30 | 2016-12-21 | 广州三飞航空科技有限公司 | One lifts unmanned plane easily |
| CN107054634A (en) * | 2017-03-23 | 2017-08-18 | 沈阳无距科技有限公司 | Multiaxis unmanned plane |
| CN108033013A (en) * | 2017-12-14 | 2018-05-15 | 邵文远 | A kind of VTOL fixed-wing unmanned plane |
| CN108058812A (en) * | 2018-01-02 | 2018-05-22 | 晨龙飞机（荆门）有限公司 | A kind of unmanned plane for possessing folded wing |
| CN108313264A (en) * | 2018-01-26 | 2018-07-24 | 易瓦特科技股份公司 | Adjustable rotor engine body system for fixed-wing unmanned plane |
| CN108974349A (en) * | 2017-05-31 | 2018-12-11 | 大鹏航太有限公司 | Simple pitching control device for aircraft capable of achieving vertical lifting and fixed wing flying |
| CN109263902A (en) * | 2018-09-18 | 2019-01-25 | 陶文英 | A kind of fixed wing aircraft direct force assisting in flying control method and system |
| WO2019090046A1 (en) * | 2017-11-03 | 2019-05-09 | Aai Corporation | Vtol aircraft having fixed-wing and rotorcraft configurations |
| CN110871892A (en) * | 2018-09-01 | 2020-03-10 | 田瑜 | Aircraft vertical stabilizer with lift propeller and method of use |
| CN111891334A (en) * | 2020-08-07 | 2020-11-06 | 山东理工大学 | An agricultural bionic bird repelling drone based on deformable wings |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB935715A (en) * | 1961-04-18 | 1963-09-04 | Boeing Co | Improvements in or relating to airplane for vertical and/or short take-off and landing |
| US20030094537A1 (en) * | 2000-07-28 | 2003-05-22 | Austen-Brown John Frederick | Personal hoverplane with four tiltmotors |
| CN102001446A (en) * | 2010-11-11 | 2011-04-06 | 韦斯豪 | Structure of vertical take-off and landing rotor aircraft |
| CN103072688A (en) * | 2013-01-22 | 2013-05-01 | 西安交通大学 | Tiltable four-rotor wing aircraft |
| CN103587683A (en) * | 2013-11-13 | 2014-02-19 | 中国航空工业集团公司西安飞机设计研究所 | Small-sized aircraft with tiltable rotor wings |
| CN203681869U (en) * | 2013-12-24 | 2014-07-02 | 西安交通大学 | Power system structure suitable for vertical take-off and landing air vehicle |
-
2013
- 2013-12-24 CN CN201310722455.XA patent/CN103738496A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB935715A (en) * | 1961-04-18 | 1963-09-04 | Boeing Co | Improvements in or relating to airplane for vertical and/or short take-off and landing |
| US20030094537A1 (en) * | 2000-07-28 | 2003-05-22 | Austen-Brown John Frederick | Personal hoverplane with four tiltmotors |
| CN102001446A (en) * | 2010-11-11 | 2011-04-06 | 韦斯豪 | Structure of vertical take-off and landing rotor aircraft |
| CN103072688A (en) * | 2013-01-22 | 2013-05-01 | 西安交通大学 | Tiltable four-rotor wing aircraft |
| CN103587683A (en) * | 2013-11-13 | 2014-02-19 | 中国航空工业集团公司西安飞机设计研究所 | Small-sized aircraft with tiltable rotor wings |
| CN203681869U (en) * | 2013-12-24 | 2014-07-02 | 西安交通大学 | Power system structure suitable for vertical take-off and landing air vehicle |
Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104494812A (en) * | 2015-01-08 | 2015-04-08 | 常州大学 | Fixed-wing air vehicle device with screw propeller having tiltable shaft |
| CN104743112A (en) * | 2015-04-24 | 2015-07-01 | 南昌航空大学 | Novel tilt wing aircraft |
| CN104743112B (en) * | 2015-04-24 | 2017-04-12 | 南昌航空大学 | Novel tilt wing aircraft |
| WO2016201661A1 (en) * | 2015-06-18 | 2016-12-22 | 罗春晖 | Lift force device for airplane, and takeoff method using device |
| CN106163925B (en) * | 2015-06-18 | 2018-06-12 | 罗春晖 | A kind of lift unit for aircraft and the takeoff method using the device |
| CN106163925A (en) * | 2015-06-18 | 2016-11-23 | 罗春晖 | A kind of lift unit for aircraft and use the takeoff method of this device |
| CN105292462A (en) * | 2015-10-30 | 2016-02-03 | 佛山市神风航空科技有限公司 | Multi-axle aircraft |
| CN105292462B (en) * | 2015-10-30 | 2017-12-05 | 佛山市神风航空科技有限公司 | A kind of Multi-axis aircraft |
| CN105460233B (en) * | 2015-11-12 | 2018-04-20 | 中国人民解放军国防科学技术大学 | One kind can VTOL Fixed Wing AirVehicle design method |
| CN105460233A (en) * | 2015-11-12 | 2016-04-06 | 中国人民解放军国防科学技术大学 | Method for designing fixed-wing aircraft capable of vertically taking off and landing |
| CN105539835A (en) * | 2016-01-18 | 2016-05-04 | 成都纵横自动化技术有限公司 | Composite-wing vertical take-off and landing aircraft |
| CN105564641A (en) * | 2016-01-29 | 2016-05-11 | 珠海市磐石电子科技有限公司 | Vector aircraft |
| CN106240812B (en) * | 2016-08-30 | 2018-08-03 | 广州三飞航空科技有限公司 | It is a kind of to lift easily unmanned plane |
| CN106240812A (en) * | 2016-08-30 | 2016-12-21 | 广州三飞航空科技有限公司 | One lifts unmanned plane easily |
| CN107054634A (en) * | 2017-03-23 | 2017-08-18 | 沈阳无距科技有限公司 | Multiaxis unmanned plane |
| CN108974349A (en) * | 2017-05-31 | 2018-12-11 | 大鹏航太有限公司 | Simple pitching control device for aircraft capable of achieving vertical lifting and fixed wing flying |
| WO2019090046A1 (en) * | 2017-11-03 | 2019-05-09 | Aai Corporation | Vtol aircraft having fixed-wing and rotorcraft configurations |
| US11724801B2 (en) | 2017-11-03 | 2023-08-15 | Textron Systems Corporation | VTOL aircraft having fixed-wing and rotorcraft configurations |
| CN108033013A (en) * | 2017-12-14 | 2018-05-15 | 邵文远 | A kind of VTOL fixed-wing unmanned plane |
| CN108058812A (en) * | 2018-01-02 | 2018-05-22 | 晨龙飞机（荆门）有限公司 | A kind of unmanned plane for possessing folded wing |
| CN108313264A (en) * | 2018-01-26 | 2018-07-24 | 易瓦特科技股份公司 | Adjustable rotor engine body system for fixed-wing unmanned plane |
| CN110871892A (en) * | 2018-09-01 | 2020-03-10 | 田瑜 | Aircraft vertical stabilizer with lift propeller and method of use |
| CN109263902A (en) * | 2018-09-18 | 2019-01-25 | 陶文英 | A kind of fixed wing aircraft direct force assisting in flying control method and system |
| CN111891334A (en) * | 2020-08-07 | 2020-11-06 | 山东理工大学 | An agricultural bionic bird repelling drone based on deformable wings |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103738496A (en) | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof | |
| CN203681869U (en) | Power system structure suitable for vertical take-off and landing air vehicle | |
| CN104290907B (en) | Novel hybrid vertical/short take off and landing unmanned vehicle | |
| CN202754143U (en) | Rotating engine vertical take-off and landing aircraft | |
| CN200995782Y (en) | Airplane | |
| CN102126553B (en) | Vertically taking off and landing small unmanned aerial vehicle | |
| CN103043212B (en) | Composite aircraft composed of fixed wing and electric multi-rotor | |
| CN202728576U (en) | Transformable composite aircraft formed by fixed wing and electric multi-propeller | |
| CN205440869U (en) | Fixed chord flight time aircraft of canard configuration of VTOL | |
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| CN102514712A (en) | Vertical take-off and landing aircraft | |
| CN104364154A (en) | Aircraft, preferably unmanned | |
| CN205022861U (en) | VTOL fixed wing aircraft | |
| CN106184741B (en) | Vertical take-off and landing unmanned aerial vehicle with flying wing type ducted fan | |
| CN204473140U (en) | New vertical landing tilting rotor two axle aircraft | |
| CN107140179B (en) | A kind of tailstock formula tandem chord endurance aerodynamic configuration of aircraft | |
| RU2635431C1 (en) | Convertible aircraft | |
| CN103786881A (en) | Tilting rotor wing helicopter | |
| RU2674622C1 (en) | Convertiplane | |
| CN105905295A (en) | Vertical take-off and landing fixed wing aircraft | |
| CN106672231A (en) | Unmanned aerial vehicle | |
| RU139040U1 (en) | AIRCRAFT "LANNER" | |
| CN106005371B (en) | Difference directly drives dynamic three rudder face unmanned planes entirely | |
| CN2923518Y (en) | Circular jet-air aircraft | |
| CN202923886U (en) | Plane with high safety |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140423 |